EP2876314B1 - Befestigungselement von Teilen einer Montageanordnung - Google Patents

Befestigungselement von Teilen einer Montageanordnung Download PDF

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Publication number
EP2876314B1
EP2876314B1 EP14193919.9A EP14193919A EP2876314B1 EP 2876314 B1 EP2876314 B1 EP 2876314B1 EP 14193919 A EP14193919 A EP 14193919A EP 2876314 B1 EP2876314 B1 EP 2876314B1
Authority
EP
European Patent Office
Prior art keywords
strips
assembly
treated
fixing element
rod
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP14193919.9A
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English (en)
French (fr)
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EP2876314A1 (de
Inventor
Jean-Philippe Maurel
Frédéric LABAL
Jean-Luc Martres
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to EP16184762.9A priority Critical patent/EP3112702B1/de
Publication of EP2876314A1 publication Critical patent/EP2876314A1/de
Application granted granted Critical
Publication of EP2876314B1 publication Critical patent/EP2876314B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/008—Corrosion preventing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/06—Surface treatment of parts furnished with screw-thread, e.g. for preventing seizure or fretting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B4/00—Shrinkage connections, e.g. assembled with the parts at different temperature; Force fits; Non-releasable friction-grip fastenings
    • F16B4/004—Press fits, force fits, interference fits, i.e. fits without heat or chemical treatment

Definitions

  • the present invention relates to a fastener of assembly parts.
  • the present invention generally applies to the field of fixing parts of an assembly, in particular for an aircraft. Such an assembly must be protected against the risks associated with lightning strikes.
  • the fastener is interfered with, and generally moderately interfered with, in the parts of the assembly.
  • It comprises a rod formed of a cylindrical barrel and a threaded end or not, the end cooperating during assembly for example with a nut or a crimping ring.
  • the cylindrical barrel has a diameter substantially larger than the bore made in the parts of the assembly and intended to receive the fastener.
  • this electrical conductivity must be sufficient and compatible with the risks associated with lightning strikes, especially when the fastening element is intended for an aircraft assembly disposed near a fuel zone, for example at the level of the wing of an aircraft.
  • Such a protective cap (also called in English terminology “ nup cap ”) is described in the document WO 2012/118855 .
  • Fixing elements are also known which provide good electrical conductivity by applying a surface treatment of the rod by anodic oxidation.
  • fasteners providing good electrical conductivity by anodic oxidation of their surface are difficult to install with moderate interference.
  • the document FR 2,855,386 discloses a fastener according to the preamble of claim 1, in particular an anodic oxidation treated sputter coated with a phenolic coating to protect the fastener from corrosion.
  • the present invention aims to solve at least one of the aforementioned drawbacks.
  • the present invention relates to a fastener of parts of an assembly as defined by claim 1.
  • the fastener comprises a rod formed of a cylindrical barrel and one end, the rod being a metal part treated at least partially at the surface by anodic oxidation.
  • the rod is coated on at least a portion of the cylindrical barrel with a lubricating coating.
  • the cylindrical barrel has three first strips extending in the length of said cylindrical barrel and surface-treated by anodic oxidation, and three second strips extending in the length of said cylindrical barrel and coated with said lubricant coating.
  • Such a fastener does not require the use of a protective cap to protect the fastener against the risks associated with lightning strikes.
  • the present invention also relates to an assembly comprising at least two parts fixed to one another by a fastener element according to the invention, mounted in interference.
  • the invention also relates to an aircraft comprising at least one such assembly.
  • the fastening element 10 comprises a rod 11 formed of a cylindrical drum 12 and an end 13.
  • the end 13 of the rod 11 is a threaded end adapted to cooperate with a nut. (not shown in Figures 1A, 1B and 1 C ).
  • the rod 11 is also provided with a head 14 located at the end opposite the threaded end 13 of the rod 11.
  • the cylindrical barrel 12 is of diameter substantially greater than the diameter of the threaded end 13 so that the rod 11 comprises a frustoconical portion 15 of connection between the cylindrical barrel 12 and the end 13.
  • the fastening element 10 is a metal part, and for example can be made of titanium.
  • titanium is particularly preferred for its properties of conductivity and corrosion resistance.
  • the head 14 and the end 13 of the rod 11 are coated with a lubricating coating R.
  • the cylindrical shaft 12 comprises both a portion coated with a lubricating coating R and a surface-treated portion by anodic oxidation O or the like.
  • the cylindrical barrel 12 comprises two anodically oxidized surface-treated strips O and two strips coated with a lubricant coating R.
  • the anodically oxidized surface-treated strips O and the lubricious coating strips R extend over angular sectors at the periphery of the cylindrical drum 12.
  • the anodically oxidized surface-treated strips O and the strips coated with a lubricating coating R are distributed uniformly at the periphery of the cylindrical drum 12.
  • the two anodically oxidized surface-treated strips O respectively extend over two 90 ° angular sectors and the two strips coated with the lubricant coating R respectively extend over two angular sectors of 90 °.
  • the anodic oxidation treatment of the rod 11 may be a sulfuric anodic oxidation (OAS) treatment.
  • OFS sulfuric anodic oxidation
  • Anodic oxidation treatment provides good electrical conductivity to the rod 11 and in particular to the cylindrical shaft 12 of the fastening element 10.
  • the implementation of the treatment method will require the use of a mask or mask on the parts of the fastener not subject to anodic oxidation treatment.
  • the thickness of the surface treatment by anodic oxidation is equal to about 0.5 microns.
  • the lubricant coating R is a non-limiting example of a coating based on phenolic resin.
  • It may for example be composed of a phenolic resin-based coating incorporating anticorrosive pigments and / or lubricating pigments.
  • Such a coating is in particular marketed under the trademark HI-KOTE®, and for example under the name HI-KOTE® 1NC.
  • the lubricating coating R Since only a part of the fastening element 10, and in particular of the rod 11, is coated with the lubricating coating R, the latter will be applied, for example by spraying or dipping, using a mask or mask. protection applied to the portions of the rod 11 not coated with the lubricant coating R.
  • This lubricant coating R on the rod 11 is substantially equal to 5 microns.
  • the cylindrical barrel 12 comprises on 50% of its external surface anodic oxidation treatment O.
  • the cylindrical barrel 12 comprises an anodically oxidized surface-treated strip O and a strip coated with the lubricating coating R
  • the arrangement of the longitudinal strips around the cylindrical barrel 12 is not limited to the embodiment previously described. .
  • cylindrical shaft 12 may comprise only an anodically oxidized surface-treated strip O and a strip coated with the lubricant coating R, these strips thus extending over an angular sector of 180 °.
  • cylindrical barrel 12 comprises two anodically oxidized surface-treated strips O and two strips coated with a lubricating coating R, these strips may not extend over identical 90 ° angular sectors. .
  • the two strips coated with a lubricant coating R may extend respectively on angular sectors of between 30 and 90 °, the two anodic oxidation treated strips respectively extending over angular sectors of between 90 and 150.degree. °.
  • the two strips coated with a lubricating coating R may extend respectively on angular sectors of between 90 and 150 °, the two anodic oxidation-treated strips extending respectively over angular sectors of between 30 and 90 °. .
  • the number of bands treated by anodic oxidation O and the number of strips coated with the lubricant coating R is not limited to two but may be greater, and in particular equal to three or four.
  • Figures 2 and 3 alternative embodiments.
  • the cylindrical shaft 12 comprises three anodically oxidized zones O extending respectively over angular sectors of 45 ° and separated in pairs by strips coated with a lubricating coating R respectively extending over angular sectors of 75 °. .
  • the cylindrical barrel 12 also comprises three anodically oxidized surface-treated strips O and three strips coated with a lubricating coating R.
  • the longitudinal strips are uniformly distributed at the periphery of the cylindrical barrel 12, extending respectively on angular sectors of 60 °.
  • the fastening element 10 has parts similar to those described above with reference to the Figures 1A and 1B , bearing the same numerical references.
  • the head 14 and the end 13 of the rod 11 of the fixing element 10 are surface-treated by anodic oxidation O.
  • the cylindrical barrel 12 comprises a surface treated portion by anodic oxidation O and a portion coated with a lubricating coating R.
  • the surface treatment of the fastener may be a sulfuric anodic oxidation (OAS) treatment.
  • OFS sulfuric anodic oxidation
  • the lubricant coating may be a HI-KOTE® coating.
  • the longitudinal strip arrangement of the cylindrical barrel portions 12 treated by anodic oxidation O and portions of the cylindrical barrel 12 coated with the lubricating coating R may be similar to that described above with reference to FIGS. Figures 1A, 1B , 1C, 2 and 3 .
  • the fastening element 10 comprises a rod 11 and a head 14 surface-treated integrally by anodic oxidation O.
  • the rod 11 is then coated on at least a portion of the cylindrical drum 12 with a lubricating coating R.
  • the lubricant coating R is applied both to a portion of the cylindrical drum 12, the end 13 and the connection zone 15 of the rod 11.
  • the lubricating coating R is applied in a plurality of annular bands on the rod 11 of the fastening element 10.
  • the fastening element 10 comprises two annular portions of a lubricating coating R, one disposed at the end of the cylindrical barrel 12, adjacent to the connection zone 15 and the other disposed at mid-length of the cylindrical barrel 12 in the longitudinal direction X of the cylindrical shaft 12.
  • the number of annular portions and their relative disposition in the longitudinal direction X of the fastener 10 may be variable.
  • the surface treatment of the fastener may be a sulfuric anodic oxidation treatment.
  • the lubricant coating may be a HI-KOTE® coating.
  • the fastening element 10 thus described according to different embodiments makes it possible to fix at least two pieces P1, P2, as illustrated in FIG. figure 7 in an assembly.
  • This assembly of two pieces P1, P2 may correspond to the junction panels of an aircraft.
  • the stacked parts constituting the assembly are preferably made of composite material, made from a mixture of fibers and resin.
  • the composite material can be made from a matrix made of aluminum reinforced with carbon fibers.
  • the fastening element 10 cooperates in known manner with a nut 20 mounted on the threaded end 13.
  • the nut 20 comes into contact with one of the pieces P1, P2 of the assembly, and here the last piece P2 of the assembly.
  • the fastener 10 when the end 13 of the rod 11 is not threaded, the fastener 10 is mounted according to a staple principle, using a crimped shear attachment.
  • the surface portions treated by anodic oxidation ensure the electrical continuity between the fixing element 10 and the parts P1, P2, thus ensuring the protection of the assembly against phenomena related to lightning strikes, particularly at the level of the head 14 of the fastening element 10.
  • the surface occupied by the lubricant coating R on the rod portion 11 housed in the last assembly part, and here the piece P2, does not exceed 50% of the internal surface of the bore made in the last piece P2.
  • the width of the lubricant coating R in the longitudinal direction X of the fastener element 10 is less than or equal to half of the thickness of the last assembly piece P2, also measured along the longitudinal direction X of the fastening element 10.
  • the cumulative surface area of the lubricating coating strips R is less than or equal to 50% of the annular portion of the barrel. cylindrical 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Lubricants (AREA)
  • Prevention Of Electric Corrosion (AREA)
  • Insertion Pins And Rivets (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
  • Sliding-Contact Bearings (AREA)
  • Clamps And Clips (AREA)

Claims (9)

  1. Element zur Befestigung von Teilen (P1, P2) einer Baugruppe, aufweisend eine Stange (11), welche von einem zylindrischen Schaft (12) und einem Ende (13) gebildet wird, wobei die Stange (11) ein Metallteil ist, welches zumindest teilweise durch anodische Oxidation (0) oberflächenbehandelt und über zumindest einen Abschnitt des zylindrischen Schaftes (12) mit einer gleitfähigen Beschichtung (R) beschichtet ist, dadurch gekennzeichnet, dass der zylindrische Schaft (12) erste Bänder, welche sich in der Länge des zylindrischen Schaftes (12) erstrecken und durch anodische Oxidation (0) oberflächenbehandelt sind, und zweite Bänder umfasst, welche sich in der Länge des zylindrischen Schaftes (12) erstrecken und mit der gleitfähigen Beschichtung (R) beschichtet sind, wobei die Anzahl an ersten Bändern ausschließlich gleich drei ist und die Anzahl an zweiten Bändern ausschließlich gleich drei ist.
  2. Befestigungselement nach Anspruch 1, dadurch gekennzeichnet, dass sich die ersten und zweiten Bänder über Winkelsegmente, welche über den Umfang des zylindrischen Schaftes (12) verteilt sind, erstrecken.
  3. Befestigungselement nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die ersten und zweiten Bänder gleichmäßig über den Umfang des zylindrischen Schaftes (12) verteilt sind.
  4. Befestigungselement nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass sich die durch anodische Oxidation (0) oberflächenbehandelten drei ersten Bänder jeweils über drei Winkelsegmente von 45° erstrecken und paarweise durch ein mit der gleitfähigen Beschichtung (R) beschichtetes zweites Band getrennt sind, welches sich über ein Winkelsegment von 75° erstreckt.
  5. Befestigungselement nach Anspruch 3, dadurch gekennzeichnet, dass die durch anodische Oxidation (0) oberflächenbehandelten drei ersten Bänder und die mit einer gleitfähigen Beschichtung (R) beschichteten drei zweiten Bänder sich jeweils über Winkelsegmente von 60° erstrecken.
  6. Befestigungselement nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Stange (11) zumindest teilweise durch schwefelige, anodische Oxidation behandelt ist.
  7. Befestigungselement nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die gleitfähige Beschichtung (R) eine auf Phenolharz basierende Beschichtung ist.
  8. Baugruppe, aufweisend mindestens zwei Teile (P1, P2), welche durch ein mit Presspassung montiertes Befestigungselement (10) miteinander befestigt sind, dadurch gekennzeichnet, dass das Befestigungselement (10) einem der vorhergehenden Ansprüchen entspricht.
  9. Luftfahrzeug, aufweisend mindestens eine Baugruppe nach Anspruch 8.
EP14193919.9A 2013-11-25 2014-11-19 Befestigungselement von Teilen einer Montageanordnung Active EP2876314B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16184762.9A EP3112702B1 (de) 2013-11-25 2014-11-19 Befestigungselement von teilen einer montageanordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1361603A FR3013781A1 (fr) 2013-11-25 2013-11-25 Element de fixation de pieces d'un assemblage

Related Child Applications (2)

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EP16184762.9A Division EP3112702B1 (de) 2013-11-25 2014-11-19 Befestigungselement von teilen einer montageanordnung
EP16184762.9A Division-Into EP3112702B1 (de) 2013-11-25 2014-11-19 Befestigungselement von teilen einer montageanordnung

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EP2876314A1 EP2876314A1 (de) 2015-05-27
EP2876314B1 true EP2876314B1 (de) 2017-08-30

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Country Status (7)

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US (2) US10072695B2 (de)
EP (2) EP3112702B1 (de)
JP (1) JP6523660B2 (de)
CN (1) CN104653557B (de)
CA (1) CA2870858C (de)
FR (1) FR3013781A1 (de)
RU (1) RU2671905C2 (de)

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US20150147136A1 (en) 2015-05-28
FR3013781A1 (fr) 2015-05-29
EP3112702A1 (de) 2017-01-04
RU2014147206A (ru) 2016-06-10
EP3112702B1 (de) 2019-08-28
CN104653557A (zh) 2015-05-27
JP6523660B2 (ja) 2019-06-05
US10072695B2 (en) 2018-09-11
US20190024697A1 (en) 2019-01-24
EP2876314A1 (de) 2015-05-27
CA2870858A1 (fr) 2015-05-25
CA2870858C (fr) 2022-03-01
JP2015102247A (ja) 2015-06-04
RU2671905C2 (ru) 2018-11-07
CN104653557B (zh) 2018-12-14

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